Combustor panels having recessed rail

Abstract

A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

What is claimed is: 
     
       1. A method of manufacturing a combustor of a gas turbine engine comprising:
 mounting a first panel to an interior surface of a combustor shell at a first position, the combustor shell defining a combustion chamber, the first panel comprising:
 a first end; 
 a first rail proximate the first end; 
 a first combustion chamber surface extending axially within the combustion chamber from the first rail to an axially opposite end of the first panel, the first combustion chamber surface being parallel with the interior surface of the combustor shell, the first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell; and 
 a first extension of the first combustion chamber surface extending axially from the first rail to the first end of the first panel; 
 
 mounting a second panel to the interior surface of the combustor shell at a second position and axially adjacent to the first panel, the second panel comprising:
 a second end; 
 a second rail proximate the second end; 
 a second combustion chamber surface extending from the second rail to an axially opposite end of the second panel, the second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell; and 
 a second extension of the second combustion chamber surface extending axially from the second rail to the second end of the second panel, 
 
 wherein the first end and the second end are proximal to each other and define a circumferentially extending gap therebetween, 
 wherein the first rail, the second rail, the first extension, and the second extension collectively define an impingement cooling volume at the circumferentially extending gap, and 
 wherein the combustor shell includes at least one impingement aperture proximate the circumferentially extending gap, the at least one impingement aperture being configured to provide impingement cooling air to the impingement cooling volume. 
 
     
     
       2. The method of  claim 1 , wherein the first rail extends a first distance from the first combustion chamber surface toward the interior surface of the combustor shell, and the first extension extends a second distance, wherein the second distance is between one quarter and seven times the first distance. 
     
     
       3. A combustor for a gas turbine engine comprising:
 a combustor shell having an interior surface and defining a combustion chamber having an axial length; 
 a first panel mounted to the interior surface of the combustor shell at a first position, the first panel having comprising:
 a first end; 
 a first rail proximate the first end; 
 a first combustion chamber surface extending axially within the combustion chamber from the first rail to an axially opposite end of the first panel, the first combustion chamber surface being parallel with the interior surface of the combustor shell, the first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell; and 
 a first extension of the first combustion chamber surface extending axially from the first rail to the first end of the first panel; 
 
 a second panel mounted to the interior surface of the combustor shell at a second position and axially adjacent to the first panel, the second panel comprising:
 a second end; 
 a second rail proximate the second end; 
 a second combustion chamber surface extending from the second rail to an axially opposite end of the second panel, the second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell; and 
 a second extension of the second combustion chamber surface extending axially from the second rail to the second end of the second panel, 
 
 wherein the first end of the first panel and the second end of the second panel are proximal to each other and define a circumferentially extending gap therebetween, 
 wherein the first rail, the second rail, the first extension, and the second extension collectively define an impingement cooling volume at the circumferentially extending gap, and 
 wherein the combustor shell includes at least one impingement aperture proximate the circumferentially extending gap, the at least one impingement aperture being configured to provide impingement cooling air to the impingement cooling volume. 
 
     
     
       4. The combustor of  claim 3 , wherein the first rail extends a first distance from the first combustion chamber surface toward the interior surface of the combustor shell, and the first extension extends a second distance, wherein the second distance is between one quarter and seven times the first distance. 
     
     
       5. The combustor of  claim 3 , wherein the first extension has a length of between 0.08 inches and 0.12 inches. 
     
     
       6. The combustor of  claim 3 , further comprising a plurality of first panels and a plurality of second panels, wherein circumferentially adjacent panels of the plurality of first panels define respective axially extending gaps therebetween and wherein circumferentially adjacent panels of the plurality of second panels define respective axially extending gaps therebetween. 
     
     
       7. The combustor of  claim 6 , wherein each first panel of the plurality of first panels includes at least one axially extending rail that extends from the first rail along the axially extending gap. 
     
     
       8. A gas turbine engine comprising:
 a combustor including a combustor shell, the combustor shell having an interior surface and defining a combustion chamber having an axial length; 
 a first panel mounted to the interior surface of the combustor shell at a first position, the first panel comprising:
 a first end; 
 a first rail proximate the first end; 
 a first combustion chamber surface extending axially within the combustion chamber from the first rail to an axially opposite end of the first panel, the first combustion chamber surface being parallel with the interior surface of the combustor shell, the first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell; and 
 a first extension of the first combustion chamber surface extending axially from the first rail to the first end of the first panel; 
 
 a second panel mounted to the interior surface of the combustor shell at a second position and axially adjacent to the first panel, the second panel comprising:
 a second end; 
 a second rail proximate the second end; 
 a second combustion chamber surface extending from the second rail to an axially opposite end of the second panel, the second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell; and 
 a second extension of the second combustion chamber surface extending axially from the second rail to the second end of the second panel, 
 
 wherein the first end of the first panel and the second end of the second panel are proximal to each other and define a circumferentially extending gap therebetween, 
 wherein the first rail, the second rail, the first extension, and the second extension collectively define an impingement cooling volume at the circumferentially extending gap, and 
 wherein the combustor shell includes at least one impingement aperture proximate the circumferentially extending gap, the at least one impingement aperture being configured to provide impingement cooling air to the impingement cooling volume. 
 
     
     
       9. The gas turbine engine of  claim 8 , wherein the first rail extends a first distance from the first combustion chamber surface toward the interior surface of the combustor shell, and the first extension extends a second distance, wherein the second distance is between one quarter and seven times the first distance. 
     
     
       10. The gas turbine engine of  claim 8 , wherein the first extension has a length of between 0.08 inches and 0.12 inches. 
     
     
       11. The gas turbine engine of  claim 8 , further comprising a plurality of first panels and a plurality of second panels, wherein circumferentially adjacent panels of the plurality of first panels define respective axially extending gaps therebetween and wherein circumferentially adjacent panels of the plurality of second panels define respective axially extending gaps therebetween. 
     
     
       12. The gas turbine engine of  claim 11 , wherein each first panel of the plurality of first panels includes at least one axially extending rail that extends from the first rail along the axially extending gap.